LOW-THRUST LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER

摘要

FIELD: machine building. ^ SUBSTANCE: proposed combustion chamber comprises mixing head with oxidiser and propellant jet nozzles communicated with aft-of-valve chambers and having extra chambers in combustion chamber walls or inside. In compliance with this invention, said extra chambers are made up of loop channels with jet nozzles at outlet extending to wedge-type mixer surface. Said loop channels may be made up of capillary tubes arranged inside combustion chamber while wedge-type mixer may represent a cone. ^ EFFECT: higher operating performances. ^ 3 cl, 1 dwg